BR112012015862B8 - wear reduction system in a gas turbine combustion system and method to reduce wear in a gas turbine combustion system - Google Patents

wear reduction system in a gas turbine combustion system and method to reduce wear in a gas turbine combustion system

Info

Publication number
BR112012015862B8
BR112012015862B8 BR112012015862A BR112012015862A BR112012015862B8 BR 112012015862 B8 BR112012015862 B8 BR 112012015862B8 BR 112012015862 A BR112012015862 A BR 112012015862A BR 112012015862 A BR112012015862 A BR 112012015862A BR 112012015862 B8 BR112012015862 B8 BR 112012015862B8
Authority
BR
Brazil
Prior art keywords
gas turbine
wear
turbine combustion
combustion system
shaped block
Prior art date
Application number
BR112012015862A
Other languages
Portuguese (pt)
Other versions
BR112012015862A2 (en
BR112012015862B1 (en
Inventor
Pietrangeli Emanuele
Del Puglia Eugenio
Cappuccini Filippo
Romanelli Marco
Giannozzi Massimo
Original Assignee
Nuovo Pignone Spa
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by Nuovo Pignone Spa filed Critical Nuovo Pignone Spa
Publication of BR112012015862A2 publication Critical patent/BR112012015862A2/en
Publication of BR112012015862B1 publication Critical patent/BR112012015862B1/en
Publication of BR112012015862B8 publication Critical patent/BR112012015862B8/en

Links

Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
    • F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
    • F02C7/20—Mounting or supporting of plant; Accommodating heat expansion or creep
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B32—LAYERED PRODUCTS
    • B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
    • B32B15/00—Layered products comprising a layer of metal
    • B32B15/04—Layered products comprising a layer of metal comprising metal as the main or only constituent of a layer, which is next to another layer of the same or of a different material
    • B32B15/043—Layered products comprising a layer of metal comprising metal as the main or only constituent of a layer, which is next to another layer of the same or of a different material of metal
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B32—LAYERED PRODUCTS
    • B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
    • B32B5/00—Layered products characterised by the non- homogeneity or physical structure, i.e. comprising a fibrous, filamentary, particulate or foam layer; Layered products characterised by having a layer differing constitutionally or physically in different parts
    • B32B5/16—Layered products characterised by the non- homogeneity or physical structure, i.e. comprising a fibrous, filamentary, particulate or foam layer; Layered products characterised by having a layer differing constitutionally or physically in different parts characterised by features of a layer formed of particles, e.g. chips, powder or granules
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D9/00—Stators
    • F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D9/00—Stators
    • F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
    • F01D9/023—Transition ducts between combustor cans and first stage of the turbine in gas-turbine engines; their cooling or sealings
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
    • F23R3/42—Continuous combustion chambers using liquid or gaseous fuel characterised by the arrangement or form of the flame tubes or combustion chambers
    • F23R3/60—Support structures; Attaching or mounting means
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2230/00—Manufacture
    • F05D2230/20—Manufacture essentially without removing material
    • F05D2230/23—Manufacture essentially without removing material by permanently joining parts together
    • F05D2230/232—Manufacture essentially without removing material by permanently joining parts together by welding
    • F05D2230/237—Brazing
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2300/00—Materials; Properties thereof
    • F05D2300/20—Oxide or non-oxide ceramics
    • F05D2300/22—Non-oxide ceramics
    • F05D2300/226—Carbides
    • F05D2300/2263—Carbides of tungsten, e.g. WC
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
    • Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
    • Y10T428/00—Stock material or miscellaneous articles
    • Y10T428/12—All metal or with adjacent metals
    • Y10T428/12014—All metal or with adjacent metals having metal particles
    • Y10T428/12028—Composite; i.e., plural, adjacent, spatially distinct metal components [e.g., layers, etc.]
    • Y10T428/12063—Nonparticulate metal component
    • Y10T428/12139—Nonmetal particles in particulate component

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Wood Science & Technology (AREA)
  • Life Sciences & Earth Sciences (AREA)
  • Powder Metallurgy (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Carbon And Carbon Compounds (AREA)
  • Ceramic Products (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Coating By Spraying Or Casting (AREA)

Abstract

sistema para redução de desgaste em um sistema de combustão de um turbina a gás, método para reduzir o desgaste em um sistema de combustão de uma turbina a gás e material sólido resistente ao desgaste a presente invenção referem-se à proteção ao desgaste e, mais particularmente, à adição de insertos em ferragens de combustão em sistemas de turbina a gás. o sistema para redução de desgaste em um sistema de combustão de uma turbina a gás compreende pelo menos um bloco em formato de h (202) configurado para prender uma peça de transição (10) de um combustor de turbina a gás em uma peça de suporte (214); um primeiro inserto (602, 702) que inclui um primeiro carboneto de tungstênio em uma primeira matriz de metal, em que a dita primeira matriz de metal é selecionada a partir de um grupo que compreende cobalto e níquel; e um primeiro material de brasagem (710) entre o dito pelo menos um bloco em formato de h (202) e o dito primeiro inserto (602, 702), o dito primeiro material de brasagem (710) é configurado para realizar brasagem do dito primeiro inserto (602, 702) no dito pelo menos um bloco em formato de h em pelo menos uma localização em uma superfície de desgaste interior do dito pelo menos um bloco em formato de h (202), em que a dita superfície interior do dito pelo menos um bloco em formato de h (202) inclui uma primeira superfície (606) perpendicular a uma segunda superfície (608) que perpendicular a uma terceira superfície (610), sendo que a dita terceira superfície (610) é paralela e tem uma área de superfície igual à dita primeira superfície (606).wear reduction system in a gas turbine combustion system, method to reduce wear in a gas turbine combustion system and wear resistant solid material the present invention refers to wear protection and, more particularly, the addition of combustion hardware inserts in gas turbine systems. the wear reduction system in a gas turbine combustion system comprises at least one h-shaped block (202) configured to secure a transition piece (10) of a gas turbine combustion to a support piece (214); a first insert (602, 702) which includes a first tungsten carbide in a first metal matrix, wherein said first metal matrix is selected from a group comprising cobalt and nickel; and a first brazing material (710) between said at least one h-shaped block (202) and said first insert (602, 702), said first brazing material (710) is configured to braze said first insert (602, 702) in said at least one h-shaped block in at least one location on an interior wear surface of said at least one h-shaped block (202), wherein said interior surface of said at least one h-shaped block (202) includes a first surface (606) perpendicular to a second surface (608) which is perpendicular to a third surface (610), said third surface (610) being parallel and having a surface area equal to said first surface (606).

BR112012015862A 2009-12-15 2010-12-09 wear reduction system in a gas turbine combustion system and method to reduce wear in a gas turbine combustion system BR112012015862B8 (en)

Applications Claiming Priority (3)

Application Number Priority Date Filing Date Title
ITCO2009A000065A IT1396884B1 (en) 2009-12-15 2009-12-15 INSERTS IN TUNGSTEN CARBIDE AND METHOD
ITCO2009S000065 2009-12-15
PCT/EP2010/069239 WO2011073075A2 (en) 2009-12-15 2010-12-09 Tungsten carbide inserts and method

Publications (3)

Publication Number Publication Date
BR112012015862A2 BR112012015862A2 (en) 2016-06-21
BR112012015862B1 BR112012015862B1 (en) 2020-08-11
BR112012015862B8 true BR112012015862B8 (en) 2020-09-01

Family

ID=42340695

Family Applications (1)

Application Number Title Priority Date Filing Date
BR112012015862A BR112012015862B8 (en) 2009-12-15 2010-12-09 wear reduction system in a gas turbine combustion system and method to reduce wear in a gas turbine combustion system

Country Status (10)

Country Link
US (1) US20130199193A1 (en)
EP (1) EP2513563B1 (en)
KR (1) KR20120092711A (en)
CN (1) CN102741615B (en)
AU (1) AU2010333066B2 (en)
BR (1) BR112012015862B8 (en)
CA (1) CA2784957A1 (en)
IT (1) IT1396884B1 (en)
RU (1) RU2549755C2 (en)
WO (1) WO2011073075A2 (en)

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US20150068212A1 (en) * 2012-04-19 2015-03-12 General Electric Company Combustor liner stop
CA2924550C (en) 2013-10-17 2019-02-12 Halliburton Energy Services, Inc. Particulate reinforced braze alloys for drill bits
US10571126B2 (en) 2017-02-08 2020-02-25 General Electric Company Method to provide a braze coating with wear property on micromixer tubes
MA51338A (en) * 2017-12-19 2021-03-31 Weir Minerals Australia Ltd COMPOSITE METAL COMPONENT AND ITS PRODUCTION PROCESS

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Also Published As

Publication number Publication date
KR20120092711A (en) 2012-08-21
CN102741615A (en) 2012-10-17
EP2513563A2 (en) 2012-10-24
BR112012015862A2 (en) 2016-06-21
CA2784957A1 (en) 2011-06-23
BR112012015862B1 (en) 2020-08-11
US20130199193A1 (en) 2013-08-08
AU2010333066A1 (en) 2012-07-12
WO2011073075A3 (en) 2011-08-25
RU2012126744A (en) 2014-01-27
ITCO20090065A1 (en) 2011-06-16
RU2549755C2 (en) 2015-04-27
IT1396884B1 (en) 2012-12-20
CN102741615B (en) 2014-12-17
WO2011073075A2 (en) 2011-06-23
AU2010333066B2 (en) 2016-07-14
EP2513563B1 (en) 2016-08-10

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Legal Events

Date Code Title Description
B06F Objections, documents and/or translations needed after an examination request according [chapter 6.6 patent gazette]
B06U Preliminary requirement: requests with searches performed by other patent offices: procedure suspended [chapter 6.21 patent gazette]
B09A Decision: intention to grant [chapter 9.1 patent gazette]
B09W Correction of the decision to grant [chapter 9.1.4 patent gazette]

Free format text: RETIFICACAO NO PARECER DE DEFERIMENTO DO DESPACHO 9.1 NA RPI 2566.

B16A Patent or certificate of addition of invention granted [chapter 16.1 patent gazette]

Free format text: PRAZO DE VALIDADE: 20 (VINTE) ANOS CONTADOS A PARTIR DE 09/12/2010, OBSERVADAS AS CONDICOES LEGAIS.

B16C Correction of notification of the grant [chapter 16.3 patent gazette]

Free format text: REF. RPI 2588 DE 11/08/2020 QUANTO A PRIORIDADE UNIONISTA.

B21F Lapse acc. art. 78, item iv - on non-payment of the annual fees in time

Free format text: REFERENTE A 11A ANUIDADE.

B24J Lapse because of non-payment of annual fees (definitively: art 78 iv lpi, resolution 113/2013 art. 12)

Free format text: EM VIRTUDE DA EXTINCAO PUBLICADA NA RPI 2648 DE 05-10-2021 E CONSIDERANDO AUSENCIA DE MANIFESTACAO DENTRO DOS PRAZOS LEGAIS, INFORMO QUE CABE SER MANTIDA A EXTINCAO DA PATENTE E SEUS CERTIFICADOS, CONFORME O DISPOSTO NO ARTIGO 12, DA RESOLUCAO 113/2013.